Abstract. The Small Whiskbroom Imager for atmospheric compositioN monitorinG (SWING) is a compact remote sensing instrument dedicated to mapping trace gases from an unmanned aerial vehicle (UAV). SWING is based on a compact visible spectrometer and a scanning mirror to collect scattered sunlight. Its weight, size, and power consumption are respectively 920 g, 27 cm × 12 cm × 8 cm, and 6 W. SWING was developed in parallel with a 2.5 m flying-wing UAV. This unmanned aircraft is electrically powered, has a typical airspeed of 100 km h −1 , and can operate at a maximum altitude of 3 km.We present SWING-UAV experiments performed in Romania on 11 September 2014 during the Airborne ROmanian Measurements of Aerosols and Trace gases (ARO-MAT) campaign, which was dedicated to test newly developed instruments in the context of air quality satellite validation. The UAV was operated up to 700 m above ground, in the vicinity of the large power plant of Turceni (44.67 • N, 23.41 • E; 116 m a.s.l.). These SWING-UAV flights were coincident with another airborne experiment using the Airborne imaging differential optical absorption spectroscopy (DOAS) instrument for Measurements of Atmospheric Pollution (AirMAP), and with ground-based DOAS, lidar, and balloon-borne in situ observations.The spectra recorded during the SWING-UAV flights are analysed with the DOAS technique. This analysis reveals NO 2 differential slant column densities (DSCDs) up to 13 ± 0.6 × 10 16 molec cm −2 . These NO 2 DSCDs are converted to vertical column densities (VCDs) by estimating air mass factors. The resulting NO 2 VCDs are up to 4.7 ± 0.4 × 10 16 molec cm −2 . The water vapour DSCD measurements, up to 8 ± 0.15 × 10 22 molec cm −2 , are used to estimate a volume mixing ratio of water vapour in the boundary layer of 0.013 ± 0.002 mol mol −1 . These geophysical quantities are validated with the coincident measurements.

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Abstract. The Small Whiskbroom Imager for atmospheric compositioN monitorinG (SWING) is a compact remote sensing instrument dedicated to mapping trace gases from an Unmanned Aerial Vehicle (UAV). SWING is based on a compact visible spectrometer and a scanning mirror to collect scattered sunlight. Its weight, size, and power consumption are respectively 920 g, 27 x 12 x 8 cm3, and 6 W. SWING was developed in parallel with a 2.5 m flying wing UAV. This unmanned aircraft is electrically powered, has a typical airspeed of 100 km h−1, and can operate at a maximum altitude of 3 km. We present SWING-UAV experiments performed in Romania on 11 September 2014 during the Airborne ROmanian Measurements of Aerosols and Trace gases (AROMAT) campaign. The UAV was operated up to 700 m above ground, in the vicinity of the large power plant of Turceni (44.67° N, 23.41° E, 116 m a.s.l.). These SWING-UAV flights were coincident with another airborne experiment using the Airborne imaging Differential Optical Absorption Spectroscopy (DOAS) instrument for Measurements of Atmospheric Pollution (AirMAP), and with ground-based DOAS, lidar, and balloone-borne in-situ observations. The spectra recorded during the SWING-UAV flights are analyzed with the DOAS technique. This analysis reveals NO2 differential slant column densities (DSCDs) up to 13 ± 0.6 x 1016 molec cm−2. These NO2 DSCDs are converted to vertical column densities (VCDs) by estimating air mass factors. The resulting NO2 VCDs are up to 4.7 ± 0.4 x 1016 molec cm−2. The water vapor DSCD measurements, up to 8 ± 0.15 x 1022 molec cm−2, are used to estimate a volume mixing ratio of water vapor in the boundary layer of 0.013 ± 0.002 mol mol−1. These geophysical quantities are validated with the coincident measurements.

The paper shows a full 6 DOF modeling for a GRAD rocket in Earth's non-inertial frame. For numerical purposes the modeling is limited to flat Earth approximation. The full motion equations are shown and all terms are explained together with the aerodynamics parameters for the entire flight envelope. Non-linear interpolation is used for aerodynamic coefficients and their derivatives. We present the typical dispersion factors due to rocket production inaccuracies, launch condition variability and atmospheric factors and their relative influence on a guidance implementation package.Next we present a 6 DOF modeling with various step-like thrust-curves while maintain the same total impulse delivered by the original motor. The influence of the step size on the range of the GRAD rocket is investigated together with the dispersion influence. We show that significant range increase can be obtained while using the same propulsion unit with a steplike thrust-curve modification. We also investigate the influence of the step-like thrust-curve on dispersion of such a rocket and the technological possibilities to implement our solution.In the last part of the paper we present a terminal guidance concept 122 mm rockets. A preliminary requirement for IMU units to be used for terminal guidance is shown together with the general guidance algorithm for several trajectories. Performance expectations are shown through the analysis of the IMU units performance as well as flight dynamics of the 122 mm rockets.